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	Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints 期刊论文 OAI收割 International Journal of Automation and Computing, 2018, 卷号: 15, 期号: 2, 页码: 218-227 作者: Hui-Bo Zhou; Jun-Hong Song; Shen-Min Song \| 收藏 \| 浏览/下载：17/0 \| 提交时间：2021/02/23 Autopilot impact angle nonsingular terminal sliding mode finite-time convergent guidance.
	Reentry guidance based on parametric optimization (EI CONFERENCE) 会议论文 OAI收割 2012 International Conference on Mechatronics and Control Engineering, ICMCE 2012, November 29, 2012 - November 30, 2012, Guangzhou, China 作者: Li D. 收藏 \| 浏览/下载：161/0 \| 提交时间：2013/03/25 This paper presents a parametric optimization approach to solve reentry guidance. Due to the various constraints imposed on the trajectory original guidance problem can be converted into an optimal control problem with a merit function to be minimized. Direct implementation of method of variation and is too complex to get a reasonable result while a numerical parametric optimization approach is feasible and efficient if we choose appropriate control variables as the optimization parameters and effective optimization algorithm. A simulation of the approach is performed to show its validity on reentry guidance problem: as the value of merit function converges to acceptable threshold all constraints are hold. (2013) Trans Tech Publications Switzerland.
	High gain observer for drag tracking in mars entry longitudinal guidance (EI CONFERENCE) 会议论文 OAI收割 2012 International Conference on Measurement, Instrumentation and Automation, ICMIA 2012, September 15, 2012 - September 16, 2012, Guangzhou, China Wu K.; Cui H.; Ma D.; Cui P. 收藏 \| 浏览/下载：28/0 \| 提交时间：2013/03/25 An extended high gain state and perturbation observer combined with feedback linearization was applied in drag tracking for Mars entry longitudinal guidance. The observer estimates the drag the drag rate and the perturbation due to model uncertainty and disturbance for drag tracking. Mars entry simulation was performed to assess the performance of the adaptive guidance law. The results demonstrate that the proposed guidance law is robust to model error and can recover the ideal performance of the feedback linearization control. Introduction In recent years the concept of pinpoint landing has been proposed (2013) Trans Tech Publications Switzerland.
	Reentry guidance based on feedback linearization (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Electronics, Communications and Control, ICECC 2011, September 9, 2011 - September 11, 2011, Ningbo, China Li D.-W. 收藏 \| 浏览/下载：30/0 \| 提交时间：2013/03/25 This paper presents a new reentry guidance algorithm for RLV (Reusable Launching Vehicle). The algorithm consists of two integrated components: trajectory planning algorithm and tracking algorithm. The most striking feature of algorithm here lies in that both planning and tracking are executed directly in height-velocity space which is different from the methodology of configuration of drag in traditional shuttle guidance. In the session of trajectory planning all trajectory constraints can be expressed with upper bound and lower bound in height-velocity space then a linear interpolation is carried to search the nominal trajectory satisfying the requirement of downrange and target constraints. Then the tracking algorithm uses feedback linearization method to track this nominal profile and meet all constraints. Another typical feature of this algorithm is the strategy of downrange extension using FPA (flight path angle) controller to fulfill the requirement of large downrange. Proper combination of planning-tracking algorithm and FPA controller can bring great flexibility and adaptability to reentry guidance. The algorithm is proved to be robust enough to accommodate the model error and noises in the dynamics. 2011 IEEE.
	LOS rate reconstruction and application of roll-pitch seeker (EI CONFERENCE) 会议论文 OAI收割 2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China Yang C.; Zhang N.; Jia H. 收藏 \| 浏览/下载：22/0 \| 提交时间：2013/03/25 Frame motion form of roll-pitch seeker is introduced in this paper. There is corresponding relationship between the frame angle of the roll-pitch seeker and the traditional yaw-pitch seeker. The discrepancy of line-of-sight (LOS) rate of the two seekers is caused by the different frame motion forms. LOS rate reconstruction method of roll-pitch seeker is deduced. Compared to the pure proportional navigation guidance law the true proportional navigation guidance law is more suitable for the roll-pitch seeker missile guidance. 2011 IEEE.